A star unfolding mechanism

Abstract

The present application provides a star unfolding mechanism, comprising a rotating structure for rotatingly connecting a main star body and a sub-star module; and a locking structure for locking the position of the sub-star module relative to the main star body; the locking structure comprises a slide rod fixedly combined with the main star body, a connecting rod rotatably connected to one end of the sub-star module, a slide seat rotatably connected to the other end of the connecting rod, and a locker fixedly combined with the slide seat; the slide seat is sleeved on the slide rod and can move along the extension direction of the slide rod; the slide seat comprises a locking position; the locker is configured such that when the slide seat moves to the locking position on the slide rod, the locker can lock and fix the slide seat on the slide rod, thereby locking the position of the sub-star module relative to the main star body. The star unfolding mechanism can reliably unfold and lock the satellite star unfolding module, and provide high-rigidity support, so that the entire satellite platform achieves high rigidity.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology. More specifically, it relates to a celestial deployment mechanism. Background Technology

[0002] With the continuous development of commercial spaceflight, the need to reduce the size of satellites, increase their surface area to the Earth and the sky, and increase their rigidity within the limited space of rocket fairings is becoming increasingly prominent. This is to ensure that flutter caused by satellite attitude or orbital maneuvers can be quickly attenuated, which is conducive to the rapid stabilization of satellite payloads and high-precision observation and imaging. Furthermore, the smaller size of the satellite body in its launch state and its retracted state can meet the requirements of launching multiple satellites with one rocket, further reducing launch costs. Summary of the Invention

[0003] To address the aforementioned problems, this invention provides a satellite deployment mechanism that can reliably deploy and lock the satellite deployment module, and provides high-rigidity support, enabling the entire satellite platform to achieve high rigidity and facilitating orbital maneuver control. Simultaneously, it increases the satellite platform's surface area relative to the Earth and space, expands the space available for payload installation, provides a wider field of view, and reduces the number of related devices required.

[0004] To achieve the above objectives, the present invention adopts the following technical solution:

[0005] This invention provides a celestial deployment mechanism, comprising:

[0006] Rotational structures used to rotatably connect the main star and the sub-star modules; and

[0007] A locking structure used to lock the position of the sub-satellite module relative to the main body;

[0008] The locking structure includes a slide rod fixed to the main body, a connecting rod rotatably connected to the sub-satellite module at one end, a slide block rotatably connected to the other end of the connecting rod, and a locker fixed to the slide block.

[0009] The slide block is fitted onto the slide rod and can move along the extension direction of the slide rod; the slide block includes a locking position;

[0010] The locking device is configured to lock the slide block to the slide rod when the slide block moves to the locked position, thereby locking the position of the sub-satellite module relative to the main body.

[0011] Furthermore, in a preferred embodiment, the locking device includes a rotating pin fixed to the slide block, a first clipper and a second clipper rotatably connected to the rotating pin, and a torsion spring providing clamping force to the first clipper and the second clipper; the locking device abuts against the surface of the slide rod via the first clipper and the second clipper, and the locking device can move along the extension direction of the slide rod with the slide block;

[0012] The slide bar has an annular groove formed by an inward indentation of a portion of its surface.

[0013] When the slide block moves to the locked position on the slide rod, the first and second clippers of the locking device will engage and fix the slide block on the annular groove, thereby locking the slide block onto the slide rod.

[0014] Furthermore, in a preferred embodiment, the first clipper includes a first snap-fit ​​portion, a first rotating portion, and a connecting portion that connects the first snap-fit ​​portion and the first rotating portion;

[0015] The second clipper includes a second snap-fit ​​portion and a second rotating portion fixed to the second snap-fit ​​portion;

[0016] The first latching part and the second latching part are in the same plane;

[0017] The rotating pin passes through both the first rotating part and the second rotating part.

[0018] Furthermore, in a preferred embodiment, the torsion spring is sleeved on the rotating pin and located between the first rotating part and the second rotating part;

[0019] The torsion spring includes a first torsion arm fixedly connected to a first rotating part and a second torsion arm fixedly connected to a second rotating part.

[0020] Furthermore, in a preferred embodiment, the slide bar is fixed to the main body via a fixing seat; the number of fixing seats is two; and both ends of the slide bar are respectively connected and fixed to the fixing seats.

[0021] Furthermore, in a preferred embodiment, the star deployment mechanism further includes a fixed hinge seat configured on the sub-star module for rotatably mounting the connecting rod.

[0022] Furthermore, in a preferred embodiment, the end of the connecting rod for connecting with the slide is formed with a through hole; the slide includes a mating portion; and the mating portion is formed with a mounting hole for engaging with the through hole.

[0023] The locking structure also includes a pivot for passing through both the through hole and the mounting hole; the connecting rod is rotatable about the axis of the pivot.

[0024] Furthermore, in a preferred embodiment, the surface of the slide rod located between the two fixed seats is a smooth surface.

[0025] Furthermore, a preferred embodiment is that the deployment angle of the celestial body deployment mechanism is in the range of 0-90°.

[0026] Furthermore, in a preferred embodiment, the rotating structure includes two hinges configured to rotatably connect the primary star and the sub-star module.

[0027] The beneficial effects of this invention are as follows:

[0028] This invention rotatably connects the main satellite and the sub-satellite module through a rotating structure, and cooperates with a locking structure. When the slide block moves to the locked position on the slide rod, the locking device can lock the slide block to the slide rod, thereby locking the position of the sub-satellite module relative to the main satellite. This enables reliable deployment and locking of the satellite deployment module, while providing high-rigidity support, making the entire satellite platform more rigid and facilitating orbital maneuver control. It also increases the satellite platform's surface area to the sky and the ground, increases the space available for payload installation, provides a wider field of view, and reduces the number of related equipment required. In the launch state, this satellite deployment mechanism can compactly retract the satellite deployment module into the main satellite, reducing the launch space required. Attached Figure Description

[0029] The specific embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0030] Figure 1 This is a schematic diagram of the deployed state of the celestial body deployment mechanism of the present invention.

[0031] Figure 2 This is a schematic diagram of the stellar deployment mechanism of the present invention in its retracted state.

[0032] Figure 3 This is a schematic diagram of the installation of the slide of the present invention.

[0033] Figure 4 This is a schematic diagram of the locking mechanism of the present invention.

[0034] Figure 5 This is a schematic diagram of the torsion spring of the present invention.

[0035] Figure 6 This is a schematic diagram of the cooperation between the slide bar and the fixed seat of the present invention. Detailed Implementation

[0036] Various exemplary embodiments of the present invention will now be described in detail with reference to the accompanying drawings. It should be noted that, unless otherwise specifically stated, the relative arrangement, numerical expressions, and values ​​of the components and steps set forth in these embodiments do not limit the scope of the invention.

[0037] The following description of at least one exemplary embodiment is merely illustrative and is in no way intended to limit the invention or its application or use.

[0038] Technologies and equipment known to those skilled in the art may not be discussed in detail, but where appropriate, such technologies and equipment should be considered part of the specification.

[0039] In all the examples shown and discussed herein, any specific values ​​should be interpreted as merely exemplary and not as limitations. Therefore, other examples of exemplary embodiments may have different values.

[0040] It should be noted that similar labels and letters in the following figures indicate similar items; therefore, once an item is defined in one figure, it does not need to be discussed further in subsequent figures.

[0041] To minimize the satellite's launch envelope and maximize its surface area above and below Earth after orbit insertion, while simultaneously maintaining the overall rigidity of the satellite platform for easy maneuverability and rapid stabilization, this invention provides a satellite deployment mechanism, combining... Figures 1 to 6 As shown, the specific celestial deployment mechanism includes: a rotating structure for rotatably connecting the main celestial body 1 and the sub-celestial module 2; and a locking structure for locking the position of the sub-celestial module 2 relative to the main celestial body 1. The locking structure includes a slide rod 8 fixed to the main celestial body 1, a connecting rod 11 rotatably connected at one end to the sub-celestial module 2, a slide block 9 rotatably connected to the other end of the connecting rod 11, and a locking device 13 fixed to the slide block 9. The slide block 9 is sleeved on the slide rod 8 and can move along the extension direction of the slide rod 8. The slide block 9 includes a locked position; in this embodiment, when the slide block 9 is in the locked position, the main celestial body 1 and the sub-celestial module 2 are perpendicular to each other. Figure 1 As shown, the side surface of the main satellite 1 is perpendicular to the top surface of the sub-satellite module 2. The locking device 13 is configured to lock the slide 9 onto the slide rod 8 when the slide 9 moves to the locked position, thereby locking the position of the sub-satellite module 2 relative to the main satellite 1. The satellite deployment mechanism described in this invention can be adaptively modified according to different satellite envelope sizes and weights, and can also be used to improve the deployment stiffness of large space deployment mechanisms such as antennas and solar panels. It should be noted that the satellite deployment mechanism may include two sets of locking structures, which are symmetrically arranged on both sides of the satellite, further improving the stability and stiffness of the satellite after deployment.

[0042] This invention utilizes a locking structure, including a connecting rod 11, a sliding block 9, and a sliding rod 8, in conjunction with the satellite body. This allows for rigid support of a large satellite body with relatively small structural mass. Specifically, the sliding rod 8 is arranged vertically. Once the relative positions between the main satellite body 1 and the sub-satellite module 2 are determined (i.e., the satellite body is fully deployed), the connecting rod 11 and the sliding rod 8 form a triangular support structure with the horizontal plane, achieving stable support for the satellite body.

[0043] In one specific embodiment, the locking device 13 includes a rotating pin 14 fixed to the slide block 9, a first clipper 15 and a second clipper 16 rotatably connected to the rotating pin 14, and a torsion spring 17 providing clamping force to the first clipper 15 and the second clipper 16. The locking device 13 is fixed to the bottom surface of the slide block 9 by the rotating pin 14, and the locking device 13 abuts against the surface of the slide rod 8 by the first clipper 15 and the second clipper 16. The locking device 13 can move with the slide block. 9 moves along the extension direction of the slide bar 8, meaning that the locking device 13 is clamped on the slide bar 8 and can slide up and down on the slide bar 8; the slide bar 8 has an annular groove 19 formed by a portion of the surface of the slide bar 8 being recessed inward; when the slide block 9 moves to the locked position on the slide bar 8, the first clipper 15 and the second clipper 16 of the locking device 13 will approach each other horizontally under the elastic restoring force of the torsion spring 17, and then engage and fix them on the annular groove 19, thereby locking the slide block 9 to the slide bar 8. The present invention uses the above-mentioned scissor-type locking device 13, and the moving direction of the slide block 9 is perpendicular to the locking direction of the locking device 13, so that external disturbances will not cause a decrease in locking stiffness.

[0044] Furthermore, the first clipper 15 includes a first engaging portion, a first rotating portion, and a connecting portion connecting the first engaging portion and the first rotating portion; the inclined connecting portion ensures that the first rotating portion and the first engaging portion are not in the same plane; the second clipper 16 includes a second engaging portion and a second rotating portion fixed to the second engaging portion; the first engaging portion and the second engaging portion are in the same plane, and both the first engaging portion and the second engaging portion are curved to match the outer surface of the slide bar, ensuring that the first engaging portion and the second engaging portion can be simultaneously engaged into the annular groove to achieve a circumferential locking; the rotating pin 14 passes through both the first rotating portion and the second rotating portion.

[0045] More specifically, the torsion spring 17 is sleeved on the rotating pin 14 and located between the first rotating part and the second rotating part; the torsion spring 17 includes a first torsion arm fixedly connected to the first rotating part and a second torsion arm fixedly connected to the second rotating part, and the first rotating part and the second rotating part rotate around the axis of the rotating pin through the torsional force of the torsion spring 17. It should be noted that the locking device 13 of the present invention only requires a very small torque from the torsion spring 17 to reliably lock the unfolding mechanism, without causing excessive resistance to the movement of the slide 9.

[0046] In one specific embodiment, the slide rod 8 is fixed to the main body 1 by a fixing seat; there are two fixing seats; both ends of the slide rod 8 are respectively fixed to the fixing seats, namely the upper fixing seat 6 and the lower fixing seat 7. In this invention, the movement limit of the slide block 9 along the slide rod 8 also relies on the limit of the bottom surface of the upper fixing seat 6 to ensure that the locking device 13 can stably achieve the circumferential locking. Both fixing seats are installed on the main body by screws, and a fixing interface for fixing the slide rod 8 is reserved to fix the two ends of the slide rod 8. An annular groove 19 is provided at a distance of one slide block height from the upper fixing seat 6 on the slide rod 8. Specifically, when the sub-satellite module 2 is unfolded to 90°, the upper surface of the slide block 9 touches the lower surface of the upper fixed seat 6. At this time, the first clipper 15 and the second clipper 16 of the locking device 13 are locked into the annular groove 19 of the slide rod 8 under the action of the torsion spring 17. At this time, the position of the locking device 13 and the slide block 9 fixed thereto relative to the slide rod 8 is completely restricted, and the rotational freedom of the connecting rod 11 relative to the fixed hinge seat 12 and the slide block 9 is completely restricted. At this time, the entire unfolding mechanism achieves rigid support for the satellite after unfolding into place.

[0047] In one specific embodiment, the satellite deployment mechanism further includes a fixed hinge seat 12 for rotatably mounting the connecting rod 11 on the sub-satellite module 2. The fixed hinge seat 12 is mounted on the sub-satellite module 2 by screws and hinged to one end of the connecting rod 11, and the connecting rod 11 has a certain degree of rotational freedom relative to the fixed hinge seat 12.

[0048] Regarding the connection method between the connecting rod 11 and the slide 9, specifically, the end of the connecting rod 11 used to connect with the slide 9 has a through hole; the slide 9 includes a mating part; the mating part has a mounting hole for mating with the through hole; the locking structure also includes a rotating shaft 10 for passing through both the through hole and the mounting hole; the connecting rod 11 can rotate about the axis of the rotating shaft 10. The slide 9 is mounted on the slide rod 8 and can slide relative to the slide rod 8 in the up-down direction. Its bottom surface is fixed with a locking device 13 by a rotating pin 14. A mating part for mounting the rotating shaft 10 is reserved on the left side. The rotating shaft 10 connects the connecting rod 11 and the slide 9, and provides the connecting rod 11 with rotational freedom relative to the slide 9.

[0049] In one specific embodiment, the surface of the slide rod 8 located between the two fixed seats is a smooth surface. During the deployment of the celestial body, the first clipper 15 and the second clipper 16 are attached to the smooth surface of the middle part of the slide rod 8 by the action of the torsion spring 17. After the celestial body is deployed, the torsion spring 17 pushes the first clipper 15 and the second clipper 16 into the pre-reserved annular groove 19 on the slide rod 8 to achieve locking.

[0050] In one specific embodiment, the rotating structure includes two hinges, a left hinge 4 and a right hinge 5. The hinges are configured to rotatably connect the main satellite 1 and the sub-satellite module 2. The deployment angle range of the satellite deployment mechanism is 0-90°. Each hinge connects to the main satellite 1 on one side and the sub-satellite module 2 on the other, providing the deployment driving torque of the sub-satellite module 2 relative to the main satellite 1. Its deployment angle range is 90°. When the deployment reaches 90°, the locking mechanism on the hinge can achieve a locked position. During the satellite deployment process, driven by the two hinges, the sub-satellite module 2 performs a deployment movement relative to the main satellite 1. At this time, the slide 9 on the satellite deployment mechanism slides upward along the slide rod 8. One end of the connecting rod 11 moves upward with the slide 9 and rotates around the axis of the rotating shaft 10, while the other end rotates around the fixed hinge 12. Figure 1 and Figure 2 As shown, the sub-satellite module 2 slowly changes from a vertical state to a parallel state relative to the bottom surface of the main body 1. When the sub-satellite module 2 is deployed to the 90° position, the two hinges lock simultaneously. At the same time, the first clipper 15 and the second clipper 16 of the locking device 13, which is fixed to the slide block 9 by the rotating pin 14, rotate towards each other under the action of the torsion spring 17 and engage in the pre-reserved annular groove 19 on the slide rod 8. This achieves the locking of the slide block 9 along the longitudinal direction of the slide rod 8. At this time, the satellite deployment mechanism is completely locked and forms a stable triangular structure with the connecting rod 11, the slide rod 8 and the edges of the sub-satellite module 2, ensuring sufficient locking rigidity.

[0051] In summary, this invention rotatably connects the main satellite and the sub-satellite module through a rotating structure, and cooperates with a locking structure. When the slide block moves to the locked position on the slide rod, the locking device can lock the slide block to the slide rod, thereby locking the position of the sub-satellite module relative to the main satellite. This enables reliable deployment and locking of the satellite deployment module, while providing high-rigidity support, making the entire satellite platform more rigid and facilitating orbital maneuver control. It also increases the satellite platform's surface area to the sky and the ground, increases the space available for payload installation, provides a wider field of view, and reduces the number of devices required. In launch mode, this satellite deployment mechanism can compactly retract the satellite deployment module into the main satellite, reducing the launch space required.

[0052] Obviously, the above embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the implementation of the present invention. For those skilled in the art, other variations or modifications can be made based on the above description. It is impossible to exhaustively list all the implementation methods here. All obvious variations or modifications derived from the technical solutions of the present invention are still within the protection scope of the present invention.

Claims

1. A celestial deployment mechanism, characterized in that, include: A rotating structure used to connect the main star and the sub-star modules; as well as A locking structure used to lock the position of the sub-satellite module relative to the main body; The locking structure includes a slide rod fixed to the main body, a connecting rod rotatably connected to the sub-satellite module at one end, a slide block rotatably connected to the other end of the connecting rod, and a locker fixed to the slide block. The slide block is fitted onto the slide rod and can move along the extension direction of the slide rod; the slide block includes a locking position; The locking device is configured to lock the slide block to the slide block when the slide block moves to the locking position on the slide rod, thereby locking the position of the sub-satellite module relative to the main satellite. The locking device includes a rotating pin fixed to the slide, a first clipper and a second clipper rotatably connected to the rotating pin, and a torsion spring that provides clamping force to the first clipper and the second clipper; the locking device abuts against the surface of the slide rod through the first clipper and the second clipper, and the locking device can move along the extension direction of the slide rod with the slide. The slide bar has an annular groove formed by an inward indentation of a portion of its surface. When the slide block moves to the locked position on the slide rod, the first and second clippers of the locking device will engage and fix the slide block on the annular groove, thereby locking the slide block onto the slide rod.

2. The celestial deployment mechanism according to claim 1, characterized in that, The first clipper includes a first snap-fit ​​part, a first rotating part, and a connecting part that connects the first snap-fit ​​part and the first rotating part; The second clipper includes a second snap-fit ​​portion and a second rotating portion fixed to the second snap-fit ​​portion; The first latching part and the second latching part are in the same plane; The rotating pin passes through both the first rotating part and the second rotating part.

3. The celestial deployment mechanism according to claim 2, characterized in that, The torsion spring is sleeved on the rotating pin and located between the first rotating part and the second rotating part; The torsion spring includes a first torsion arm fixedly connected to a first rotating part and a second torsion arm fixedly connected to a second rotating part.

4. The celestial deployment mechanism according to claim 1, characterized in that, The slide bar is fixed to the main body by a fixing seat; there are two fixing seats; both ends of the slide bar are respectively connected and fixed to the fixing seats.

5. The celestial deployment mechanism according to claim 1, characterized in that, The satellite deployment mechanism also includes a fixed hinge seat for rotatably mounting the connecting rod on the sub-satellite module.

6. The celestial deployment mechanism according to claim 1, characterized in that, The end of the connecting rod for connecting with the slide has a through hole; the slide includes a mating part; the mating part has a mounting hole for engaging with the through hole; The locking structure also includes a pivot for passing through both the through hole and the mounting hole; the connecting rod is rotatable about the axis of the pivot.

7. The celestial deployment mechanism according to claim 1, characterized in that, The surface of the slide rod located between the two fixed seats is a smooth surface.

8. The celestial deployment mechanism according to claim 1, characterized in that, The deployment angle range of the celestial body deployment mechanism is 0-90°.

9. The celestial deployment mechanism according to claim 1, characterized in that, The rotating structure includes two hinges configured to rotatably connect the primary star and the sub-star module.

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